Aeroplane.



H. L., A. B. & 11.0. SHORT.

' AEBOPLANE.

I APPLICATION FILED JUNE 21, 1910. 1,002,002, Patented Aug. 29, 1911.

3 BHEETSBHEET 1.

H. L., A. E. & H. 0. SHORT. AERO PLANE.

I APPLIOATIONIILED JUNE 21, 1910. 1,002,602. v Patented Aug. 29, 1911.

3 SHEETS-SHEET 2.

H. L., A. E. 8;; H. 0. SHORT. AEROPLANE.

APPLICATION FILED JUNE 21, 1910.

1,002,002.. Patented Aug. 29, 1911.

- 3 SHEETS-SHEET 3.

Esq

A ST Es PATENT OFFICE HORACE Lnonaansnoar, ALBERT E-USTACE SHORT, AND HUGH os wALD SHORT, or

BATTERSEA farm, LONDON,

ENGLAND.

-. A'EBQPLANE.

Specification of Letters lat ent. Patented Aug. 29, 1911.

application filed June 21, 1910. Serial No. 568,163.

all whom it may concern:- Be it known that :we, HORACE LEONARD vented certain new SHORT, ALBERT EUSTACE Snow, and HUGH OSWALD- SHORT, subjects of the King of Great Britain, residing atBattersea Park, in the county of London, England, have inand useful Improvements in 'Aeroplanes, and'of which the following is a specification.

Var ous means have been proposed for preserving or governing the lateral balance of aeroplanes, ameans well known being the warpmg of theplanes or portions of them 13 Order t vary th angle of incidence of -.1

some portion of the said planes and thereby to produce the required turnin' movement of the planes about the longitu inal axis of the machine or vessel by which they are carried. V

- Now the object of the present invention is to provide novel or improved devices for e'fllectingand carrying out this balancing of the faeroplane about the longitudinal axis of the machine in a simple and effective manner, and whichshall'not call for the warping of the planes orfor the varying of theangle of incidence of integral portions of the said planes but which devices according to the present invention shallhave for their oflicethe varying of the lifting power of-thesaid aeroplanes upon each side of the longitudinal axis of the machine by par tially cutting off or obstructing the air supply flowing to'the forwardpart of the aeroplane surface either above or below the same, and thereby cause the greater vertical component force to. either one side'or other of the cen- "ter of'gravity of the said machine.

According to this invention, and as for example applied to that class of machine known asa bi-plane flying machine, and in which each main aeroplane is-curved: from its front edge to its rear edge, comparatively small air 0 st-ructing shields pivoted about the front edge of the main plane are provided. These shields are governed by suitable mechanical devices "operable by the aviator, and are,

whenintheir normal posi: tion edgewiseto the flying-"machine, so

be substantially inoperative. The shields edges 'of Such air shields will would be reduced and shifting of the of the liftingthe. direction of motion of. that they are or may.

tendiiiglaterally upon in contact with the forward edge of the vice, "when one side of the mainaeroplane' descends, the shields upon the opposite side would be brought to or toward their vertical positions and thereby the lifting effect the lifting power of of the higher-side of the main. aeroplane rocked toward a horizontal position abou the longitudinal axis or line of flight, and by; so opepating the said air shields on one side or the other as required, the lateral balancing effect is obtained without warping, bending, or giving motion tojparts of the main aeroplane. I The invention will be further described with reference to the accompanying drawings, whereon- Figures 1 and 2 are respectively longitudi:

nal vertical. section and part front elevation.

showing the two main aeroplanes of a biplane flying machine with somuch of our invention applied thereto as will be necessary for the purposes of this description. Fig. 3 is a longitudinal section of one of the aeroplanes showingan air shield according to this invention located with its pivots above the main aeroplane, and Fig. at is a similar view showing air shields pivoted the said aeroplane both above and below themain acroplane.

Figs. 5 and 6 are similar views showing air shieldsv hinged to the forward edge of the main aeroplane and illustrated in the POSI- tion in which they are turned to coincide and fit against the said aeroplane,- and Fig. 7

is a similar view showing'the application of two of such air shields-hinged to the edge of the aeroplane and arranged the one to be turned upwardly above the aeroplane and the other .to-.'b'e turned ownwardl-y below it. Fig. 8 is a diagrammatic plan view indicating ."a, flying machine in order to show the location ;of the air' shields when applied thereto;

The present invention 1s shown as applied to that type of machine indicated in dia gram {for instance at-Fi'g. 8,;which has an aeroplaneor aeropla es indicated at '1, 2e25- I each's'ide of a longitudinal axis, there being a suitable vertical rudder or rudders 3 for lateral steering and ahorizontal rudder or rudderstfor steerin in the vertical plane, the machine also being fitted with a suitable motor for driving a propeller or propellers 5. Such machines are further fitted with" means for lateral balancing, that is for controlling the position of the laterally extending planes about the longitudinal axis coincident with the direction of flight, and it is to these means which the present invention particularl relates and which will now be descri ed.

Referring to Figs. 1 and 2 air shields are provided, which in the example shown are pivoted .to the framework 7 of the main aeroplane, and the pivot-s 8 are so located that when the shield 6 is turned about the same in .the direction ofthe arrow, one of its edges will closely approach or contact with the forward edge of the main aeroplane 1.

Means are provided for operating the air shields 6,-that is forrocking the same about their pivots 8 as required, and although we do not limit ourselves to the precise construction of such means, yet in the drawings we have illustrated at Fig. 1 a spring 9 which tends to draw the shield 6 to its normal posiv{plane abuts against "work 7 A set of air shields 6 is pivoted on each side, of the longitudinal centerline, and

shown, in which position the. said tion as a stop' 10 on the frameeach pivot is carried in bearings in the framework and provided with an arm such as 11, which by means of, a cord 12 and a hand-lever 13 can be rocked by'the aviator to bring the air shields Qinto. moreor less a vertical position.

The air. shields are-indicated in Fig. 8 bythe numeral 14 on one side of the machine, and by the numeral 15. on the other side, andthose air shields upon one side are. operated by one hand-lever such as 13, and those on the other side by a similar hand-lever, one

F of such hand-levers being located at 16 (Fi 8) and the other hand-lever at 17, althoug the other set of air shields.

' shields marked 14:,- Fig. 8,. the airs I ields 15' theposition of such levers may be varied to suit different circumstances 'as will be well understood. 'Insteadof employing two hand-levers 16 jand 17 for adjusting the air shields '14 and 15 independently of each other, a single lever can be employed, the

- and thereby the lifting 'tion,-they obstruct the passage lifting same as an aileron With this apsurface as may y .mans. of the' hand-lever 10 cated at 17 (Fig. 8) or other suitable gear,

the aeroplane having the air shields 15, Fig. 8, would be reduced and the machine would berocked about its longitudinal axis or line of flight toward a horizontal position, and by so operating the air shields either on one s'ide'or the other as required, the lateral balancing effect of the main aeroplane or aeroplanes.

It will "be observed that when the ma: chine is in'motion withtheair shieldsin their normal position, the-air has free access'to the under andupper surface of the main aeroplane, and produces the usual lifting effect,-

effect of that si e of is obtained'and this without warping, bending or giving motion to parts but if the, air shields 6 on one side of the longitudinal center of the main aeroplane are moved toward a vertical posiof the air to the under surface of that port'on of the main aeroplane, and if the a1rshields'6 are: brought so that theiredges contact with the forward edge of the main aeroplane, the effect of that part of the aeroplane will be completely nullified, and the prop rtions of the air shields 6 should be s ii that when in this vertical position, their. lower edges shouldb'e somewhatloqer than the rear edge of the main aeroplane.

Instead ofarranging the air shields as at Figs. 1' and 2, they'may be arranged as at Fig. 3, where'they are located as indicated at 18-,above the main aeroplane, and they may be operated by means similar to thatdescribed with reference to Figs. 1 and 2.

whenv moved in the direction of the-arrow so that the free edge approaches or contacts with the front edge of the main aer0-- plane, the lifting effect .of the [main aeroplane is increased, while when in the positionshown its effect is practically neutral, although itis proposed to generally construct the air shields of a formation in longitudinal: section similar to the.mainr aeroplanes, so that they may have a small lifting effect when in 'what we have termed the neutral fosition; With such a location when one slde of the main aeroplane descends, the airshields 18 Fig. 3 on that side (located above the-main aeroplane) would be brought to or approaching their vertical In this vposition the effect is reversed-since position, and thereby the force tending to lift that side ofthe-main aeroplane would be increased. g,

The action f the air shields is not tlfe' obstructors, their ofiice being td obstruct the:

- air passing'to the surface of the main plane be. behind them. Thus by but they actas valves or obstructing the flow ofair to the lower side of'aportion of an aeroplanegfthat-portion shown both hinged to the forward edge of tially .as described and shown at Fig. 4 of shields, pivots ma areceives a less lifting eifect than ithe'hthe portion of an aeroplane the said portion is j exposed to a diminution of pressurecaused I bythe vortex action due to such obstruction.

At Fig. 4 the air shields 6 and 18' are fitted both above and" below the main aeroplane, and with this arrangement when the lifting effect of one side'of the aeroplaneis to be decreased, the lower air shields 6 on that side alone are operated 'to'bring them to or toward a vertical position, while to increase the lift of the main aeroplane upon that. side, the upper air shields 18 alone are brought to or toward a vertical position. t p

Instead of pivoting the air shields as indicated in the previous figures, it will be obvious that they may be hinged orpivoted adjacent to the forward edge of the main aeroplane, the lifting effect ofwhich they are intendedxto control, and at Fig. 5 one of the air shields 6 whose action is to; be.- equivalent to that illustrated at Fig. 1 is so shown, while at Fig-6 an air shield 18 equivalent -to that shown at Fig. 3 is illustrated so pivoted to the forward edge of the main aeroplane, and these air shields shown at Figs. 5 and 6 we form so that normally when "in their inoperativepositions they lie against the main aeroplane'and do not have any substantiabretarding effect on the flight of the machine.

At Fig. 7 the air shields 6 and 18 are the main aeroplane and operate substanthe accompanying. drawings. What we claim as our invention and desire to secure by patent is 1. An aeroplane, comprising in combina-. tion, a

shields, means located at the forward edge of sai, main plane for carrying said pivots so that the latter are parallel with said forward edge of said main plane, and operat-, ing means accessible to the aviator 'by which each shield can be turned about said pivots into a position withrelation. to said front edge of said main plane to obstruct the passage of air to the forward portion of one surface thereof to alter the lifting effect of one side or the other of said main plane to obtain lateral balance of the machine.

2. An aeroplane, comprising in combination a main plane carrying a frame, air on the forward edges of said shields; means located at the" forward edge of said main plane for carrying said pivots parallel with main plane carrying a frame, air shields, pivots on the forward edges of said said forward edge and at such a distance therefrom that the free edges of the front edge ofsaid main plane, gating meahs' accessible. to the aviator by which each shield can be turned about said ivots' into a position with relation to said ront edge of .saidmain plane to obstruct of one surface thereof to alter the lifting effect of one side or the 0 her of said main chine. 3. An aeroplane, comprising in combination a main plane carrying a frame, air shields, pivots on the forward edges of said shields, means for supporting said pivots directly upon and parallel with the, forward edge of'said main plane so thatthe free edges of the shields can be from said main plane, and operating means accessible to the aviator by which each shield can-be't-urned about said pivots into 'a position with relation to said front edge of said main plane to obstruct the passage of air to the forward portion of one surface thereof to alter the lifting effect of oneside or the other of said main plane to obtain lateral balance of the machine. .7 I

4:. An aeroplane, comprising in combination a main plane carrying a. frame, air shields, pivots on the forward edges of said shields, means for supporting said ivots below and parallel with the forwar edge of said main plane so that thefree edges of said shields can be turned to contact with the lower surface of the front edge of saidmain plane, and operating means accessible to the aviator by which each shield can be turned about its pivots into a position with relation to said main plane to obstruct the passage. of air to the forward portion of chiner v 5 'An aeroplane, comprising in combinationa main. plane carrying a frame, air shields pivots on the forward edges of said shlelds, bearin s on said frame to carry said pivots paralle with and at a distance .below said forward edge of said main plane so that the free edges of said shields can be turned tocontact withthe lower surface of the front edge of said main plane, a'stop on said frame, elastic means to normally retain said shields against said stop in a position so that said shields are approxifront edge of said main plane .to-obstruct the passage of air to the forward portion of lateral balance of the-machine.

tion a main plane carrying a frame, air

said shields when turned will contact with shields, pivots on the forward edges of'said and operthe passage of air to the'forward portion front edge of'said the lower surface thereofto obtain lateral balance of the ma-' mately parallel with said main plane, and 7 operating means accessible to the'aviator by the lower surface thereof to 'obtain 6. An aeroplane, comprising in combinaplane to obtain lateral. balance of the H184 turned away ieo shieliis, aboveand parallel'with the forward edge of said main of said shields can be turned to contact with the upper surface of the front edge of said main plane, and operating means accessible to the aviator by whicheachshield can be turned about itspivots into a position with relation to the said front edge of said mam plane to obstruct the passage of air to the forward portion of the upper surface there of to ob in fla'teral balance of the machine. 'ff,'- .Ani aeroplane, comprising in combination a rnain 'plane carrying a frame, air shields located above and below the forward edge of saidm'ain plane, pivots on the forward-edges of said shields,

posting the pivots of saidishields which are means for suplocated above the forward edge'of said main forward edges of. said shields, supporting said accessible to the aviator by which can .be turned about its pivots into a po- 66 sition-withirelation to the said -front edge of .can be turned away plane at such a distance therefrom that the free edges of said shields when turned down will contact with the upper part. of the front edge of said main plane, and, means for' supporting said shields which are located belowthe front edge of said -main "plane at suchaI-l distance therefrom that ;'the free edges ofisai'd shields when turned up will contact w-ith the lower front edge ofgsaid main plane, and operating means accessible to the aviator by which each shield can be turned about its pivots into a position with relation to the said front edge of said main plane to obstruct" the passage of air to the forward portion of the upper obtain lateral balance of the machine.

' 8; An aeroplane, comprising in combination a .main plane carrying a frame, a irshields having their surfaces normallfyin ont contact with the under-surface of the.

portion of said main plane, pivots on the means for ivots directly upon 'and parallel with the orward edge of said plane so that the free edges of said shi lds from the under-surface of said main plane,

each shield means for supporting said pivots plane :so that the'free. edges forward edges of said supporting said pivots directly upon and 7.

. can

part of the,

and lower surfaces thereof to and operating means {said lma'in plane to obstructthe passage of;

the; forward portion ,of the undersurf ce :thereof to obtain lateral balance of the machine. I

9. An aer0plan e,.compr1smg 1n combmation a main plane carrying a frame, air,

shields'having' their surfaces normally in contact with the upper surface of the front portion of said main plane,.pivots oh-the shields, means for parallel with the forward edge ofsaid main plane so that the free edges of said shields;

be turned away from the upper surface of said main plane, and operating means accessible to the aviator can be-turned about its pivots into a position with relation to the said, front edge ,of said main plane to obstruct the passage of' airrto the forward portion of the'gupper surface thereof to obtain-lateral balance of the machine. 3 o i a 10. An aeroplane, comprising in combination a main plane carrying a frame, air shields having their surfaces normallyhin contact with the upper and lower surfaces so free ledges v of said- I i turned about its pivots into a position with of both the upperand lower surfaces thereof to obtain lateral bal-lflo ance of the machine.

- In witness whereof we have hereunto set .our hands in-the presence of two witnesses. am

HORACE LEONARD SHORT. ALBERT EUSTAOE snonr. Y HUGH OSWALD snos'r.

Gmn'H'BnEwnn, I 'Wnmem A. MARsnAm. H

as i by which each shield 1 

